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Rotor assembly with internal vanes

a technology of internal vanes and rotor blades, which is applied in the direction of mechanical equipment, machines/engines, ceramic layered products, etc., can solve the problems of bore width and heat treatment of the center of the bore, and achieve the effect of improving the heat treatment efficiency and reducing the cost of heat treatmen

Active Publication Date: 2022-05-24
RTX CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes a design for a fan that has multiple vanes that extend out from a central shaft. As the vanes move out, they make space between them. This can create a larger distance between the vanes at the outer edges of the fan, which can improve its performance.

Problems solved by technology

This can result in bore widths that are so large that heat treating the center of a bore may become challenging.

Method used

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  • Rotor assembly with internal vanes
  • Rotor assembly with internal vanes
  • Rotor assembly with internal vanes

Examples

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Embodiment Construction

[0070]FIG. 1 illustrates a bladed rotor assembly 100 for rotational equipment with an axial centerline 102, which centerline 102 may be or may be coaxial with an axis of rotation (e.g., a rotational axis) of the rotor assembly 100. An example of such rotational equipment is a gas turbine engine for an aircraft propulsion system, an exemplary embodiment of which is described below in further detail with respect to FIG. 36. However, the rotor assembly 100 of the present disclosure is not limited to such an aircraft application nor a gas turbine engine application. The rotor assembly 100, for example, may alternatively be configured with rotational equipment such as an industrial gas turbine engine, a wind turbine, a water turbine or any other apparatus which includes a bladed rotor.

[0071]The rotor assembly 100 of FIG. 1 includes a plurality of rotor blades 104 and a rotor disk assembly 106. Referring to FIGS. 2 and 3, each of the rotor blades 104 may be configured as a rotor blade sin...

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PUM

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Abstract

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The first rotor disk is configured from or otherwise includes disk material. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis and axially between the first rotor disk and the second rotor disk. The vanes include a first vane, which first vane is configured from or otherwise includes vane material that is different than the disk material.

Description

[0001]This application claims priority to U.S. Patent Appln. No. 62 / 962,640 filed Jan. 17, 2020, U.S. Patent Appln. No. 62 / 962,620 filed Jan. 17, 2020, U.S. Patent Appln. No. 62 / 962,628 filed Jan. 17, 2020, U.S. Patent Appln. No. 62 / 962,635 filed Jan. 17, 2020 and U.S. Patent Appln. No. 62 / 962,636 filed Jan. 17, 2020, all of which are hereby incorporated by reference herein in their entireties.BACKGROUND OF THE DISCLOSURE1. Technical Field[0002]This disclosure relates generally to rotational equipment and, more particularly, to rotor blades and associated rotor assemblies.2. Background Information[0003]Gas turbine engine designers are continually being challenged to provide gas turbine engines with improved performance at reduced weights. One design metric being pushed to provide improved performance is increasing turbine rotational speed. As the turbine rotational speed is increased, however, rotor disk bores also increase in size in order to accommodate increasing centrifugal load...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F01D5/02F01D5/30
CPCF01D5/3007F01D5/02F05D2220/32F05D2240/24F01D5/3069F01D5/087F01D5/282F01D5/284F01D5/3084F01D21/045F05D2240/126F05D2250/14F05D2250/183F05D2250/23F05D2260/31F05D2260/36F05D2300/6033C04B35/80C04B2237/40C04B2237/76C04B2237/84C04B2237/368C04B2237/38C04B35/565C04B2235/5244C04B35/584B32B18/00Y02T50/60
Inventor ROBERGE, GARY D.
Owner RTX CORP